US7762076B2 - Attachment of a ceramic combustor can - Google Patents

Attachment of a ceramic combustor can Download PDF

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Publication number
US7762076B2
US7762076B2 US11/254,876 US25487605A US7762076B2 US 7762076 B2 US7762076 B2 US 7762076B2 US 25487605 A US25487605 A US 25487605A US 7762076 B2 US7762076 B2 US 7762076B2
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United States
Prior art keywords
section
ceramic
assembly
recited
clamp
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US11/254,876
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English (en)
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US20080010990A1 (en
Inventor
Jun Shi
Jason Lawrence
David J. Bombara
David C. Jarmon
Michael T. Weber
Richard S. Tuthill
Jeffrey D. Melman
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RTX Corp
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United Technologies Corp
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Priority to US11/254,876 priority Critical patent/US7762076B2/en
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Assigned to NAVY, SECRETARY OF THE, UNITED STATES OF AMERICA reassignment NAVY, SECRETARY OF THE, UNITED STATES OF AMERICA CONFIRMATORY LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE SERIAL NUMBER SHOULD BE 11/254876 PREVIOUSLY RECORDED ON REEL 016792 FRAME 0312. ASSIGNOR(S) HEREBY CONFIRMS THE SERIAL NUMBER INCORRECTLY LISTED AS 11/125487. Assignors: LAWRENCE, JASON, SHI, JUN, WEBER, MICHAEL T., BOMBARA, DAVID J., JARMON, DAVID C, MELMAN, JEFFREY D., TUTHILL, RICHARD S.
Priority to EP06254208.9A priority patent/EP1777461B1/fr
Priority to JP2006219114A priority patent/JP2007113906A/ja
Publication of US20080010990A1 publication Critical patent/US20080010990A1/en
Publication of US7762076B2 publication Critical patent/US7762076B2/en
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Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RTX CORPORATION reassignment RTX CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: RAYTHEON TECHNOLOGIES CORPORATION
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L25/00—Constructive types of pipe joints not provided for in groups F16L13/00 - F16L23/00 ; Details of pipe joints not otherwise provided for, e.g. electrically conducting or insulating means
    • F16L25/0072—Joints for pipes of dissimilar materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L49/00—Connecting arrangements, e.g. joints, specially adapted for pipes of brittle material, e.g. glass, earthenware
    • F16L49/02—Joints with a sleeve or socket
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L49/00—Connecting arrangements, e.g. joints, specially adapted for pipes of brittle material, e.g. glass, earthenware
    • F16L49/06—Joints in which sealing surfaces are pressed together by means of a member, e.g. swivel nut, screwed on, or into, one of the joint parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • This invention relates combustion engines and, more particularly, to a combustor assembly having a unique attachment between a ceramic combustor can and a metal section.
  • Conventional combustion engines such as those used in aircraft, utilize a combustor to ignite a mixture of fuel and compressed air to propel the aircraft.
  • a combustor to ignite a mixture of fuel and compressed air to propel the aircraft.
  • a lean mixture reduces the amount of air available to cool the combustor and increases the combustor temperature.
  • the increase in temperature may exceed a desirable operating temperature of the metal.
  • Ceramic materials provide excellent high temperature resistance and have been considered for use in combustors to resist the high temperatures.
  • the coefficient of thermal expansion of ceramics is typically much lower than that of metals, which may lead to thermal stress between parts made of ceramic and parts made of metal during operation of the aircraft engine.
  • the difference in coefficients of the thermal expansion between ceramic and metal renders typical joining methods, such as welding or bonding, ineffective.
  • This invention is a combustor assembly including a unique attachment between a metal section and a ceramic section that accommodates a thermal expansion difference between the metal and the ceramic.
  • An exemplary combustor assembly includes a metal section having an axial opening that receives the ceramic section.
  • a clamp is received around the axial opening to secure the metal section and the ceramic section together.
  • Tabs on the metal section, a gasket between the metal section and the ceramic section, and springs within the clamp deform in a radial direction to cooperatively offset the thermal expansion difference to maintain a clamping force.
  • An example method of these securing thermally mis-matched sections together includes a step of elastically deforming at least two deformation members in a radial direction to cooperatively provide an amount of deformation that is greater than a thermal expansion difference in the radial direction between a metal and a ceramic section to maintain a securing force between the sections.
  • FIG. 1 is a perspective view of an example combustion section.
  • FIG. 2 is an exploded view of selected portions of the combustion section shown in FIG. 1 .
  • FIG. 3 is a cross-sectional view of an example spring washer.
  • FIG. 4 is a schematic cross-sectional view of an attachment between a metal section and a ceramic can.
  • FIG. 1 illustrates selected portions of an example combustion section 10 used, for example, in a gas turbine engine for an aircraft.
  • the combustor section 10 of a gas turbine engine includes an air fuel mixer 12 that supplies a mixture of air and fuel to an igniter 14 .
  • the air fuel mixer 12 and the igniter 14 are received in a metal section 16 .
  • the metal section 16 is secured to a ceramic can 18 , which receives the ignition products of the ignited fuel and air mixture.
  • the ceramic can 18 directs the ignition products through a transition duct 20 and into a turbine section (not shown) of a gas turbine engine.
  • a flame temperature distribution in the combustion section 10 is such that the front end near the igniter 14 has a relatively cool flame and the aft end near the ceramic can 18 and transition duct 20 has a relatively hot flame.
  • Utilizing the metal section 16 near the relatively cooler flame and the ceramic can 18 near the relatively hotter flame provides the benefit of reducing undesirable carbon monoxide emissions produced in previously known combustor assemblies.
  • carbon monoxide is produced during cooling of the ignition products in the combustion section 10 .
  • the ceramic material of the ceramic can 18 does not require as much cooling as a metal material. Since there is less cooling with the ceramic can 18 , less carbon monoxide is produced compared to previously known combustor assemblies that utilize a metallic can.
  • the ceramic material of the ceramic can 18 is less dense than metal and therefore reduces the weight of an aircraft utilizing a turbine jet engine with a ceramic can. Furthermore, utilizing the relatively inexpensive metal section 16 (compared to ceramic sections) near the cooler flame portion reduces the expense of the combustion section 10 .
  • FIG. 2 shows an exploded view of selected portions of the combustion section 10 .
  • the metal section 16 includes a forward portion 30 and a circular portion 32 welded to the forward portion 30 .
  • the circular portion 32 has an axial slot 34 and tabs 68 that are circumferentially contiguously arranged to provide the axial slot 34 for receiving the ceramic can 18 .
  • a clamp 36 is received around the axial slot 34 and the tabs 68 to secure the metal section 16 and the ceramic can 18 together.
  • the clamp 36 in this example includes first and second sections 38 a and 38 b that are secured together with bolts 40 a and 40 b and nuts 42 a and 42 b .
  • the clamp 36 can be made of more than two sections.
  • Springs 44 such as Bellville washers, are received onto the bolts 40 a and 40 b between the nuts 42 a and 42 b and flanges 43 of the second section 38 b .
  • the springs 44 maintain a tension on the bolts 40 a and 40 b to maintain a clamping force of the clamp 36 around the metal section 16 and ceramic can 18 , as described below.
  • the clamp 36 is relatively thin and narrow such that the clamp 36 elastically stretches when the clamping force is applied.
  • the clamp 36 is made of a relatively low thermal expansion material.
  • the clamp 36 is made of an alloy having a coefficient of thermal expansion that is approximately double that of the ceramic material forming the ceramic can 18 . This provides the benefit of reducing some of the thermal expansion difference between the clamp 36 and the ceramic can 18 to maintain the clamping load.
  • An aft end 46 of the ceramic can 18 is received through a support ring 48 , which is secured at bosses 50 a and 50 b to the transition duct 20 .
  • the support ring 48 is relatively low stiffness compared to the ceramic can 18 and therefore introduces minimal thermal stress to the ceramic can 18 in a radial direction.
  • a seal 52 such as a ceramic rope, is received between the ceramic can 18 and the support ring 48 to seal the combustion section 10 from the turbine section (not shown) of the aircraft.
  • the fit between the support ring 48 , seal 52 , and the ceramic can 18 is relatively loose such that the support ring 48 and the seal 52 do not significantly constrain axial thermal expansion of the ceramic can 18 during high temperature operation.
  • the springs 44 are domed and include an outer surface 54 and an inner surface 56 .
  • the springs 44 may be made of a high temperature alloy, such as a nickel-based alloy.
  • the springs 44 are compressed in the direction D into a nearly flat shape.
  • the springs 44 are biased to spring back to the domed shape. In the flat shape, the bias of the springs 44 to the domed shape provides a tension on the bolts 40 a and 40 b.
  • the springs 44 are stacked in parallel where the outer surfaces 54 of the springs 44 face in the same direction.
  • the springs 44 can be stacked in series where the outer surfaces 54 of consecutive springs 44 face towards each other.
  • Springs 44 stacked in parallel provide an increased tension on the bolts 40 a and 40 b
  • springs 44 stacked in series provide greater deflection at a lower tension.
  • the springs 44 are configured to deflect more upon tightening than an expected amount of thermal expansion difference between the clamp 36 and the ceramic can 18 to maintain a desired clamping load over a variety of temperature ranges. Given this description, one of ordinary skill will be able to recognize appropriate spring 44 configurations to meet their particular needs.
  • the ceramic can 18 is received into the axial slot 34 between the circular portion 32 and the forward section 30 .
  • the annular section 32 is welded onto the forward section 30 .
  • the annular section 32 is machined from a solid annular ring and includes axial subslots 66 that receive the ceramic can 18 .
  • the axial subslots 66 provide compliance in a radial direction between the ceramic can 18 and the metal section 16 . This helps to secure the metal section 16 and the ceramic can 18 together.
  • the annular section 32 includes a plurality of tabs 68 that extend axially from the forward section 30 about the ceramic can 18 .
  • one of the tabs includes an opening 70 that corresponds to an opening 72 in the ceramic can 18 and to an opening 73 in the second section 38 b of the clamp 36 .
  • a pin 74 which is non-threaded is received through the openings 70 , 72 , and 73 to secure the ceramic can 18 and metal section 16 together and resist axial movement between them.
  • the pin 74 may be welded to the clamp 36 before assembly of the combustion section 10 .
  • the pin 74 is made of metal or metal alloy.
  • the pin 74 includes a cooling passage 76 that allows air to flow through. The air internally cools the pin 74 and maintains the temperature of the fastener below a desirable operating temperature of the metal or alloy.
  • a bushing 78 is received between the pin 74 and the opening 72 of the ceramic can 18 .
  • the bushing 78 evenly distributes stress between the pin 74 and the ceramic can 18 and prevents relatively large stress concentrations.
  • a gasket 80 is received between the tabs 68 and the ceramic can 18 .
  • the gasket 80 compresses in the radial direction.
  • the springs 44 , tabs 68 , and gasket 80 deflect in the radial direction. Each acts as a spring to provide a tension bias on the clamp 36 .
  • the tabs 68 bend radially inward along the direction R in FIG. 4 upon tightening the clamp 36 and tend to spring radially outward to provide the tension on the clamp 36 .
  • the gasket 80 compresses and tries to decompress, providing a tension in the radial direction on the tabs 68 , which provides a bias tension on the clamp 36 .
  • the springs 44 deflect to provide a biasing tension on the clamp 36 .
  • the metal section 16 thermally expands more than the ceramic can 18 .
  • the clamp 36 which is also made of a metal material, also thermally expands more than the ceramic can 18 .
  • the clamping force decreases.
  • the springs 44 , gasket 80 , and tabs 68 deflect by a combined amount in the radial direction that is greater than a radial thermal expansion difference between the metal section 16 and the ceramic can 18 .
  • This provides the benefit of maintaining a clamping force between the first and second sections 38 a and 38 b of the clamp 36 . That is, the metal parts thermally expand more than the ceramic part and the spring components (i.e., the tabs 68 , gasket 80 , and springs 44 ) offset the difference in thermal expansion to at least partially maintain the clamping force.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Connection Of Plates (AREA)
  • Gasket Seals (AREA)
US11/254,876 2005-10-20 2005-10-20 Attachment of a ceramic combustor can Active 2028-03-01 US7762076B2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US11/254,876 US7762076B2 (en) 2005-10-20 2005-10-20 Attachment of a ceramic combustor can
EP06254208.9A EP1777461B1 (fr) 2005-10-20 2006-08-10 Assemblage d'une chambre de combustion tubulaire
JP2006219114A JP2007113906A (ja) 2005-10-20 2006-08-11 燃焼器アッセンブリ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/254,876 US7762076B2 (en) 2005-10-20 2005-10-20 Attachment of a ceramic combustor can

Publications (2)

Publication Number Publication Date
US20080010990A1 US20080010990A1 (en) 2008-01-17
US7762076B2 true US7762076B2 (en) 2010-07-27

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EP (1) EP1777461B1 (fr)
JP (1) JP2007113906A (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090260364A1 (en) * 2008-04-16 2009-10-22 Siemens Power Generation, Inc. Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US9822650B2 (en) 2011-04-28 2017-11-21 Hamilton Sundstrand Corporation Turbomachine shroud
US9932831B2 (en) 2014-05-09 2018-04-03 United Technologies Corporation High temperature compliant metallic elements for low contact stress ceramic support
US11060727B2 (en) * 2017-10-30 2021-07-13 Doosan Heavy Industries & Construction Co., Ltd. Fuel nozzle assembly and gas turbine including the same

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FR2903171B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement a liaison par crabot pour chambre de combustion de turbomachine
US7665960B2 (en) 2006-08-10 2010-02-23 United Technologies Corporation Turbine shroud thermal distortion control
US7771160B2 (en) * 2006-08-10 2010-08-10 United Technologies Corporation Ceramic shroud assembly
US8726675B2 (en) * 2007-09-07 2014-05-20 The Boeing Company Scalloped flexure ring
US8167546B2 (en) * 2009-09-01 2012-05-01 United Technologies Corporation Ceramic turbine shroud support
US10564944B2 (en) * 2010-01-07 2020-02-18 Microsoft Technology Licensing, Llc Efficient immutable syntax representation with incremental change
DE102011016917A1 (de) 2011-04-13 2012-10-18 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit einer Halterung einer Dichtung für ein Anbauteil
JP6053948B2 (ja) * 2013-10-24 2016-12-27 三菱電機株式会社 情報処理装置及び情報処理方法及びプログラム
US9771813B2 (en) * 2014-06-26 2017-09-26 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine
CN104450498B (zh) * 2014-12-16 2017-01-18 嘉兴凯实生物科技有限公司 一种核酸提取仪
US10634349B2 (en) * 2015-08-24 2020-04-28 General Electric Company Wear pad system for turbine combustion systems and method for coupling wear pad into turbine combustion system
US9976746B2 (en) 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
US11149646B2 (en) 2015-09-02 2021-10-19 General Electric Company Piston ring assembly for a turbine engine
US10168051B2 (en) * 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
US10197278B2 (en) 2015-09-02 2019-02-05 General Electric Company Combustor assembly for a turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine

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US2839894A (en) * 1952-12-31 1958-06-24 Gen Motors Corp Supporting arrangement for a gas turbine combustion chamber
US3999376A (en) * 1973-07-05 1976-12-28 Ford Motor Company One-piece ceramic support housing for a gas turbine with a rotary regenerator
US4130375A (en) * 1975-10-14 1978-12-19 Westinghouse Canada Ltd. Vane rotator assembly for a gas turbine engine
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US4573320A (en) 1985-05-03 1986-03-04 Mechanical Technology Incorporated Combustion system
US5392596A (en) 1993-12-21 1995-02-28 Solar Turbines Incorporated Combustor assembly construction
US6200092B1 (en) * 1999-09-24 2001-03-13 General Electric Company Ceramic turbine nozzle
US6397603B1 (en) * 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner
US6655148B2 (en) * 2001-06-06 2003-12-02 Snecma Moteurs Fixing metal caps onto walls of a CMC combustion chamber in a turbomachine
US6996976B2 (en) * 2002-04-03 2006-02-14 Cleaire Advanced Emmision Controls Apparatus and method for mounting a device to a pipe
US20050050902A1 (en) * 2003-08-28 2005-03-10 Nuovo Pignone Holdings Spa Fixing system of a flame pipe or liner

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090260364A1 (en) * 2008-04-16 2009-10-22 Siemens Power Generation, Inc. Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell
US9127565B2 (en) * 2008-04-16 2015-09-08 Siemens Energy, Inc. Apparatus comprising a CMC-comprising body and compliant porous element preloaded within an outer metal shell
US9822650B2 (en) 2011-04-28 2017-11-21 Hamilton Sundstrand Corporation Turbomachine shroud
US9932831B2 (en) 2014-05-09 2018-04-03 United Technologies Corporation High temperature compliant metallic elements for low contact stress ceramic support
US10883369B2 (en) 2014-05-09 2021-01-05 United Technologies Corporation High temperature compliant metallic elements for low contact stress ceramic support
US9810434B2 (en) * 2016-01-21 2017-11-07 Siemens Energy, Inc. Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine
US11060727B2 (en) * 2017-10-30 2021-07-13 Doosan Heavy Industries & Construction Co., Ltd. Fuel nozzle assembly and gas turbine including the same

Also Published As

Publication number Publication date
EP1777461A2 (fr) 2007-04-25
EP1777461A3 (fr) 2010-08-25
EP1777461B1 (fr) 2019-11-13
JP2007113906A (ja) 2007-05-10
US20080010990A1 (en) 2008-01-17

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